Fixed wing aircraft convertible to a rotary wing aircraft



June 13, 1950 E. M. TUCKER EI'AL 2,511,025

FIXED WING AIRCRAFT CONVERTIBLE TO A ROTARY WING AIRCRAFT Filed Jan. 21, 1947 2 Sheets-Sheet l \Jmvrozes EMTuc'fier 51'. BY Tucker J1".

.7. M; Tucker June 13, 1950 E. M. TUCKER ETAL FIXED WING AIRCRAFT CONVERTIBLE TO A ROTARY WING AIRCRAFT 2 Sheets-Sheet 2 Filed Jan. 21, 1947 INVENTORS BM TuckerSz: EM Tucker Jr,

1% Tucker ML ml:

err-rs Patented June 13, 1 950 UNITED STATES PATENT OFFICE FIXED WING AIRCRAFT CONVERTIBLE TO A ROTARY WING AIRCRAFT Application January 21, 1947, Serial No. 723,242

6 Claims.

This invention relates to, and it is an object to provide, an airplane including a novel wing and engine assembly arranged for adjustment so that for take-offs and landings the airplane may function as a helicopter with revolving wings, but for flight has the wings set in conventional fixed position projecting laterally from opposite sides of the fuselage.

Another object of the invention is to provide an airplane, of the type described, wherein the wing sections are arranged for adjustment in a manner to vary the angle of incidence, or reverse the same, at the will of the pilot whereby the airplane can be operated for conventional flight or as a helicopter; said wing sections being rigid for conventional flight and rotatable as a unit for helicopter flight, selectively.

A further object of the invention is to provide an airplane, as above, wherein each wing section, adjacent its outer end, carries a motor having a propeller thereon; the propellers being of reversible pitch type whereby for conventional flight both propellers are set with like pitch, but for helicopter flight, with the wing section assembly rotating, the pitch of one propeller only is reversed. I

A further object of the invention is to provide a practical airplane, and one which will be exceedingly effective for the purpose for which it is designed.

These objects are accomplished by means of such structure and relative arrangement of parts as will fully appear by a perusal of the following specification and claims.

In the drawings:

Fig. 1 is a plan view of an airplane embodying the present invention.

Fig. 2 is a side elevation of the same with the fuselage partly broken away.

Fig. 3 is an enlarged fragmentary elevation of the mounting and control mechanism for the wing section assembly.

Fig. 4 is a cross section on line 4-4 of Fig. 3.

Referring now more particularly to the characters of reference on the drawings, the airplane includes a fuselage I having a tail assembly 2 and landing wheels 3 associated therewith, the pilot's compartment being indicated generally at 4.

The wing assembly of the airplane comprises a pair of oppositely projecting wing sections 5 and 6 initially separate from each other and from the fuselage I, being disposed in a plane above the latter.

The wing sections 5 and 6 are mounted in con- 2 nection with the fuselage I in the following manner:

A tubular mounting post I is rotatably mounted in an upstanding bearing 8 fixed within the fuselage at and depending from the top adjacent the pilot's compartment. The post 1 projects upwardly above the bearing 8 and fuselage I, and at its upper end said post is fitted with rigid oppositely projecting spindles 9. The wing sections 5 and 6 have sleeves l0 fixed therein at their adjacent end portions and extending lengthwise of said sections; the sleeves surrounding the spindles 9 in relatively rotatable but axially immovable relation.

Below the spindles 9 the post 1 includes a platform ll fixed therewith; there being a pair of power units l2, such as fluid pressure actuated power cylinders, mounted on the platform ll directly ahead of the sleeves, the latter including depending radial arms l3 pivotally connected to the actuating rod M of the corresponding power unit l2.

The power units l2 are selectively operable by the pilot through the medium of a control system, shown only in part as at [5, whereby to adjust or vary the angle of incidence of the wing sections 5 and 6, or to reverse such angle of incidence of the wing sections relative to each other, at the selection of the pilot.

While the post I is rotatably mounted in the bearing 8, it may be locked up against rotation with the wing sections 5 projecting laterally in opposite directions from the fuselage l by means of a power unit 16, such as a fluid pressure actuated power cylinder, mounted on the fuselage 1 directly ahead of the post I but below the platform II.

The power unit l6 includes a plunger I! having a roller l8 on its outer end adapted. to lockingly engage in a depression is of a locking cam 20 on said post 1. It will be seen that when the plunger 11 is advanced with the roller I8 in depression IQ of cam 20, the post 1 cannot rotate; the wing sections 5 and 6 then being disposed in a manner for conventional flight.

For helicopter flight the plunger 11 and roller 18 are retracted, permitting of free rotation of the post I and the wing sections 5 and 6 therewith as a rotative assembly.

The wing sections 5 and 6 are fitted, adjacent their outer ends, with airplane engines, indicated generally at 2| and 22, each engine including a.

projecting shaft 23 having a reversible pitch propeller 24 thereon.

For conventional flight the post 1 is locked by the power unit It against rotation, and the wing sections 5 and B are set, by the power units I2, with the same angle of incidence. Similarly, for conventional flight, the reversible pitch propellers 24 are set with like pitch. With the parts so arranged theairplane. functions in the. usual manner. a

For helicopter type flight the post 1 is released for rotation, and the wing sections 5 and 6 areadjusted, by the power units l2, with reverse angle of incidence, whereby upon rotation of the wing section assembly each Wing section imparts lift to the airplane, even though saidwing sections are rotating 180 degrees" apart; When the airplane is used as a helicopter one propeller 2.4

is set with reverse pitch so that they both tend:

to rotate the wing section assembly.

It is intended for take-offs and landings that the airplane will be set for flight as a helicopter, while flight otherwise will be as a conventional airplane.

The air foil of the wing sections 5 and fir'is'the I same adjacent the opposite edges of the-wing sections so that the latter may function correctly whether set with opposed angle of incidence as for. helicopter-flight, or with-the same angle of incidence as for conventional flight.-

The engines 2i and-22', together with their re versible pitch propellers; areregulated or controlledrby the pilot from thecompartment t by control t mechanisms of Y generally conventional type .(notsh0wn) From the foregoing description it will be readily seen that there has :beenproduced such aidevice as substantially fulfills the'objects of the invention as set forth herein.

While this specification sets forth in detail the present'and preferred construction'of the device, still in practice such deviations from suchdetail may be resorted to as do not form a departure from the spiritof the invention, as defined by the is against rotation whereby the wing sections may be set with the same or opposed angle of incidence, and engine and propeller units mounted on the wing sections; at least one of the propellers being of reversible pitch type.

2. An airplane comprising, with a fuselage, a pair of wing sections disposed in adjacent end toend relation, an upstanding post; a bearing on the fuselage intermediate its endsin which thepost is turnable, releasable means to lock the post against rotation, spindles projecting laterally in opposite directions from the post outside the:

fuselage, sleeves turnably but'axially immovably secured on the spindles, the wing sections being fixedly attached longitudinally to corresponding sleeves, means adjustably securing the'sleeves (ill 4 against rotation whereby the wing sections may be set with the same or opposed angle of incidence, and engine and propeller units mountedon the wing sections, at least one of the propellers: being of reversible pitch type; said locking meansbeing.,a notched cam on the post, and a power unit on the fuselage including a plunger adapted to project into the cam notch.

3. An airplane comprising, with a fuselage, a pair of wing sections disposed in adjacent end to end relation; an upstanding post, a bearing on the fuselage intermediate its ends in which the post is turnable, releasable means to lock the post against rotation, spindles projecting laterally in opposite directions from the post outside the fuselage, sleeves turnably but axially immovablysecured on the spindles, the wing sections being fixedly attached longitudinally to corresponding sleeves, means adjustably securing the sleeves against rotation whereby the wing sectionsmay be set with the same or opposed angle of incidence, and engine and propellerl units .mounted on the wing sections, at least one.

ofthe propellers being of reversible pitch type; saidlast named means including radial arms on the sleeves, and power units connected to said arms in operative relation butnormally holding.

the same against motion.

(i. An airplane comprising in combination; a fuselage, an upstanding rotatable post secured in the fuselage, a pair of oppositely projecting,

spindles fixed to the post adjacent its upper end,

a sleeve turnably mounted on each spindle and. heldagainst axial movement relative thereto, av wing section fixedly attached to each sleeve, an.

the-postagainst rotation or to release itfor ro-- tation, and an engine and propeller unit mounted. on each wing, at-least one of the propellers beingof the reversible pitch type.

5. A combination as in claim 4-. in which said power means comprises a platform fixed to the post, arpair of fluid pressure operated power cylinders mounted on the platform, each power cylinder being operatively connected with one. of the rods.

6. A combination as in claim 4, in which the locking means comprises a cam fixed to. the post and provided with a depression, a fluid pressure operated ram mounted onthe fuselage, anda roller on the ram engageable with the depression in the cam upon operation of the ram.

EMMITT M. TUCKER. JOSEPH M. TUCKER. EMMITT M. TUCKER, JR.-

REFERENCES CITED The following references are of record in-the' file of this patent:

UNITED STATES PATENTS 

